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S3016-095-87 (s3016-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S3016-095-87 (s3016-il)
Reynolds number: 100,000
Max Cl/Cd: 48.46 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3016-il-100000-n5.txt
Download as CSV file: xf-s3016-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3016-095-87                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4018   0.11992   0.11528  -0.0094   1.0000   0.0320
 -11.000  -0.3940   0.11630   0.11166  -0.0094   1.0000   0.0303
 -10.750  -0.4880   0.11867   0.11364  -0.0059   1.0000   0.0308
 -10.500  -0.4831   0.11473   0.10972  -0.0071   1.0000   0.0292
 -10.250  -0.4810   0.11024   0.10527  -0.0090   1.0000   0.0277
  -9.750  -0.4905   0.09681   0.09195  -0.0174   1.0000   0.0236
  -9.500  -0.4896   0.09255   0.08774  -0.0191   1.0000   0.0234
  -9.250  -0.4898   0.08808   0.08331  -0.0213   1.0000   0.0231
  -9.000  -0.4920   0.08316   0.07845  -0.0240   1.0000   0.0229
  -8.750  -0.4951   0.07815   0.07351  -0.0271   1.0000   0.0227
  -8.500  -0.5009   0.07256   0.06799  -0.0313   1.0000   0.0225
  -8.250  -0.5104   0.06610   0.06156  -0.0369   1.0000   0.0221
  -8.000  -0.5186   0.05991   0.05528  -0.0406   1.0000   0.0219
  -7.750  -0.5248   0.05438   0.04957  -0.0428   1.0000   0.0217
  -7.500  -0.5279   0.04937   0.04430  -0.0436   1.0000   0.0217
  -7.250  -0.5289   0.04473   0.03928  -0.0433   1.0000   0.0222
  -7.000  -0.5274   0.04098   0.03510  -0.0418   1.0000   0.0228
  -6.750  -0.5243   0.03803   0.03168  -0.0394   1.0000   0.0234
  -6.500  -0.5209   0.03507   0.02835  -0.0369   1.0000   0.0241
  -6.250  -0.5142   0.03257   0.02556  -0.0345   1.0000   0.0246
  -6.000  -0.4991   0.03018   0.02283  -0.0332   0.9980   0.0253
  -5.750  -0.4688   0.02769   0.01991  -0.0346   0.9914   0.0263
  -5.500  -0.4368   0.02563   0.01749  -0.0359   0.9852   0.0281
  -5.250  -0.4039   0.02414   0.01564  -0.0371   0.9793   0.0315
  -5.000  -0.3713   0.02233   0.01357  -0.0381   0.9735   0.0336
  -4.750  -0.3378   0.02086   0.01203  -0.0396   0.9686   0.0361
  -4.500  -0.3058   0.01996   0.01101  -0.0406   0.9619   0.0411
  -4.250  -0.2714   0.01891   0.00980  -0.0420   0.9568   0.0454
  -4.000  -0.2422   0.01808   0.00890  -0.0424   0.9490   0.0506
  -3.750  -0.2089   0.01725   0.00801  -0.0435   0.9432   0.0610
  -3.500  -0.1813   0.01642   0.00736  -0.0437   0.9349   0.0981
  -3.250  -0.1500   0.01562   0.00687  -0.0446   0.9288   0.1802
  -3.000  -0.1246   0.01498   0.00664  -0.0445   0.9199   0.2768
  -2.750  -0.0970   0.01428   0.00649  -0.0446   0.9130   0.4055
  -2.500  -0.0720   0.01381   0.00636  -0.0439   0.9041   0.5060
  -2.250  -0.0453   0.01342   0.00624  -0.0432   0.8963   0.6005
  -2.000  -0.0184   0.01310   0.00614  -0.0422   0.8884   0.6917
  -1.750   0.0106   0.01286   0.00608  -0.0415   0.8803   0.7809
  -1.500   0.0540   0.01270   0.00597  -0.0435   0.8743   0.8652
  -1.250   0.1044   0.01262   0.00578  -0.0474   0.8677   0.9236
  -1.000   0.1531   0.01255   0.00556  -0.0512   0.8603   0.9616
  -0.750   0.1992   0.01248   0.00534  -0.0547   0.8513   0.9914
  -0.500   0.2306   0.01244   0.00516  -0.0555   0.8410   1.0000
  -0.250   0.2527   0.01244   0.00504  -0.0541   0.8295   1.0000
   0.000   0.2745   0.01246   0.00496  -0.0528   0.8166   1.0000
   0.250   0.2966   0.01249   0.00489  -0.0515   0.8034   1.0000
   0.500   0.3190   0.01251   0.00481  -0.0502   0.7897   1.0000
   0.750   0.3416   0.01252   0.00475  -0.0489   0.7754   1.0000
   1.000   0.3646   0.01255   0.00469  -0.0476   0.7607   1.0000
   1.250   0.3878   0.01258   0.00465  -0.0464   0.7458   1.0000
   1.500   0.4112   0.01261   0.00461  -0.0453   0.7305   1.0000
   1.750   0.4348   0.01267   0.00461  -0.0442   0.7140   1.0000
   2.000   0.4586   0.01273   0.00464  -0.0431   0.6963   1.0000
   2.250   0.4825   0.01280   0.00465  -0.0421   0.6782   1.0000
   2.500   0.5066   0.01287   0.00465  -0.0410   0.6596   1.0000
   2.750   0.5306   0.01298   0.00471  -0.0400   0.6386   1.0000
   3.000   0.5547   0.01311   0.00478  -0.0390   0.6175   1.0000
   3.250   0.5788   0.01327   0.00488  -0.0380   0.5939   1.0000
   3.500   0.6027   0.01345   0.00499  -0.0370   0.5694   1.0000
   3.750   0.6265   0.01367   0.00516  -0.0361   0.5436   1.0000
   4.000   0.6502   0.01393   0.00533  -0.0351   0.5163   1.0000
   4.250   0.6736   0.01423   0.00554  -0.0342   0.4878   1.0000
   4.500   0.6968   0.01456   0.00578  -0.0333   0.4586   1.0000
   4.750   0.7198   0.01494   0.00607  -0.0324   0.4293   1.0000
   5.000   0.7426   0.01535   0.00642  -0.0315   0.4005   1.0000
   5.250   0.7652   0.01579   0.00679  -0.0306   0.3728   1.0000
   5.500   0.7876   0.01627   0.00719  -0.0297   0.3470   1.0000
   5.750   0.8099   0.01678   0.00763  -0.0288   0.3222   1.0000
   6.000   0.8321   0.01729   0.00811  -0.0280   0.2997   1.0000
   6.250   0.8539   0.01786   0.00867  -0.0271   0.2788   1.0000
   6.500   0.8759   0.01842   0.00922  -0.0263   0.2592   1.0000
   6.750   0.8975   0.01900   0.00981  -0.0254   0.2405   1.0000
   7.000   0.9187   0.01963   0.01043  -0.0246   0.2234   1.0000
   7.250   0.9395   0.02027   0.01108  -0.0236   0.2072   1.0000
   7.500   0.9604   0.02092   0.01182  -0.0227   0.1914   1.0000
   7.750   0.9808   0.02160   0.01256  -0.0218   0.1765   1.0000
   8.000   1.0007   0.02233   0.01334  -0.0208   0.1626   1.0000
   8.250   1.0200   0.02309   0.01416  -0.0198   0.1491   1.0000
   8.500   1.0385   0.02391   0.01503  -0.0187   0.1364   1.0000
   8.750   1.0560   0.02480   0.01596  -0.0175   0.1249   1.0000
   9.000   1.0732   0.02570   0.01695  -0.0163   0.1133   1.0000
   9.250   1.0899   0.02664   0.01806  -0.0150   0.1023   1.0000
   9.500   1.1052   0.02767   0.01920  -0.0136   0.0918   1.0000
   9.750   1.1187   0.02879   0.02039  -0.0121   0.0823   1.0000
  10.000   1.1299   0.02999   0.02163  -0.0105   0.0733   1.0000
  10.250   1.1408   0.03119   0.02298  -0.0088   0.0639   1.0000
  10.500   1.1487   0.03246   0.02436  -0.0069   0.0545   1.0000
  10.750   1.1537   0.03391   0.02588  -0.0048   0.0458   1.0000
  11.000   1.1549   0.03570   0.02765  -0.0029   0.0396   1.0000
  11.250   1.1583   0.03753   0.02970  -0.0012   0.0339   1.0000
  11.500   1.1540   0.04000   0.03225   0.0004   0.0303   1.0000
  11.750   1.1531   0.04244   0.03490   0.0017   0.0272   1.0000
  12.000   1.1502   0.04514   0.03775   0.0024   0.0243   1.0000
  12.250   1.1447   0.04821   0.04094   0.0027   0.0227   1.0000
  12.500   1.1357   0.05193   0.04475   0.0025   0.0215   1.0000
  12.750   1.1307   0.05549   0.04855   0.0021   0.0205   1.0000
  13.000   1.1234   0.05955   0.05282   0.0012   0.0194   1.0000
  13.250   1.1140   0.06415   0.05762  -0.0004   0.0184   1.0000
  13.500   1.1041   0.06907   0.06271  -0.0023   0.0180   1.0000
  13.750   1.0931   0.07444   0.06826  -0.0047   0.0177   1.0000
  14.000   1.0810   0.08027   0.07427  -0.0075   0.0174   1.0000
  14.250   1.0675   0.08667   0.08083  -0.0108   0.0171   1.0000
  14.500   1.0542   0.09337   0.08769  -0.0144   0.0170   1.0000
  14.750   1.0398   0.10058   0.09507  -0.0183   0.0170   1.0000
  15.000   1.0248   0.10824   0.10289  -0.0224   0.0171   1.0000
  15.250   1.0082   0.11662   0.11143  -0.0271   0.0172   1.0000
  15.500   0.9896   0.12585   0.12083  -0.0321   0.0174   1.0000
  15.750   0.9666   0.13687   0.13201  -0.0382   0.0178   1.0000
  16.000   0.9349   0.15138   0.14659  -0.0459   0.0186   1.0000
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